Abstract: Methods and systems for implementing a Jupiter aerospace mission can enable delivery of a science payload to a Jupiter orbit on a direct Earth-to-Jupiter trajectory. Solar power and use of avionics also allow a fast assembly, integration, and test process compared to past outer Solar System missions. The spacecraft can include an aerodynamic forebody, a shell, and a thermal protection system. The spacecraft can manage the radiation environment, generate solar power, and return data to Earth with a robust radio-frequency (RF) amplification and antenna gain.

Abstract: Provided herein are various examples of separable waveguide couplers. In one example, a collar element is provided to surround a member comprising a faying surface, a waveguide conduit, and alignment protrusions arranged radially about a perimeter of the faying surface, where the collar element is configured to accept insertion of a mating member comprising a mating faying surface and a mating waveguide conduit. A ball detent assembly is provided having a spring element that retains ball elements in holes formed through the collar element. The waveguide conduit and the mating waveguide conduit are configured to be aligned radially by at least engagement of the alignment protrusions with alignment channels in the mating member and restrained axially by at least engagement of the ball elements with mating divots in the mating member.